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针对高超声速飞行器再入过程中强耦合、大扰动和大范围变化的气动参数的问题,基于特征建模的思想,分析动力学方程的耦合特点,采用分散控制的方案,把原非线性动力学方程用一个二阶时变差分方程组形式的特征模型描述,建立了攻角、侧滑角和滚转角三通道特征模型,并给出了黄金分割自适应的姿态控制方法.最后,针对类X-20高超声速飞行器进行数值仿真,仿真结果充分验证了这种自适应控制器的有效性.
Aiming at the problem of strong aerodynamic parameters during hypersonic vehicle reentry, based on the idea of feature modeling, the coupling characteristics of dynamic equations were analyzed. By using the decentralized control scheme, the original nonlinear dynamics The equation is described by a characteristic model in the form of second-order time-varying difference equations, and the three-channel feature model of attack angle, side slip angle and roll angle is established and the golden section adaptive attitude control method is given.Finally, -20 hypersonic vehicle numerical simulation, simulation results fully validate the effectiveness of this adaptive controller.